Rotary wing device



Oct. 21, 1952 e. RICHARD 2,614,639

ROTARY WING DEVICE Filed Aug. 4, 1947 2 SHEETS-SHEET 1 T g V M/l/ENTU/iGILBERT RiOHARD A T70RIVEY Oct. 21, 1952 G. RICHARD 2,614,639

ROTARY WING DEVICE Filed Aug. 4, 1947 2 SHEETS--SHEET 2 ATTORNEY forpart 12.

Gilbert Richard,

-ROTAR-Y WING IDEYICEP National dEtudes & dei'ltecherches.Aeronam.

tiques, Paris, France "Application August 4, min-,iseriaiM36599;.

InEranceMay IE-JBAI firtsent invention. relateszito rotaryi-"b'ladeystemsj for use on aircraft andoffthe kiridinclud- -ing' a pluralityof.bladessmounted. to rotatex'about .an'axis parallel to the-fore-and-a'ftdirection of the aircraft .to' provide Tlre .p bject of my invention iisto provide'a systo' this time. i v

*A- preferred embodiment of my invention W111 be'hereinafter describedwith reference to .the

' accompanying drawings, given chieflyby way of ,tion; I Fig. 4 is ahorizontal section of this embodiment.

According to this embodiment, an aerodynamic 1 element including a stem1 and two blades 2-2 rigid therewith in the same manner as in a con-vventional airscrew has its stem l and an annular sliding part I! rigidtherewith longitudinally .slidable in a This casing is journalled aboutan axis XX on an axle I carried in fixed posi- "tionjby the frame 5 ofthe aircraft. Casing 3 is driven in rotation about said axis XX, '-tl110l1gh a gear wheel 4-rigid with 3.

The annular portion l2 of airscrew element 1 l--.1, 2-2 is freelyrotatable about a disc [3f eccentrically pivoted about a fixed axle l4rigid' with axle l5.

axis Y-eY to the axis Z'-Z of axle I4) is equal fto the'distance betweenaxis Z-- Z and the' axis" X-X'of axle about which casing 3 rotates.

In the embodiment shown by the drawing,

casing 3 includes a second guideway at right angles-to the first one andin which are guided the elements la and l2a of a second aerodynamic bothlift and. propulsion.

rotary casing 3 forming a-slideway :The eccentricity of disc l3(distance from its item'pf this-kind wh chb ttsra edt th'e'requirementsof practice than thosexused up I aerodynamic reactions on one aerofoilcross section of one blade of such a system;

i With such aconstruction, when asing; 3

rotates about on axle, 'l 5; aerodynamic'iur'ilt 1 +2 isgivenadoublemovement', to wit:

-a.--'A rotation, together with .(zasing 3, about .b.+-A 'reciprocatingrectilinear f'tran'slatory movement in-- casingkg in synchronism.witli';'the

mo m nt oi ro a ion h wfxwith :of oscillation'equal totheperiod ofrotatiomofs'aid casing 3.

Consequently, supposing for instanc that casing 3 rotates in theanti-clockwise direction,'every aerofoil section si of the blade 2 onthe lefthand side of axis YY is moving at a speed 171 higher than that mof the similar but inversely inclined aerofoil section s: of the otherblade 2 located at the same distance from YY on the righthand sidethereof, since the angular velocity is the same for all points but thedistance from the axis of rotation XX is always greater on 1 thelefthand side than on the righthand side (see Fig. 3) due to thereciprocating translatory movement of element l2 in casing 3.

Fig. 1' shows aerodynamic reactions on the first mentioned aerofoilsection. The translatory velocity of the aircraft T (in the fore-and-aftdirection of axis XX) composed with the tangential velocity of sections1 gives a resultant velocity Pi for section $1. The chord of section s1makes an angle ii with Pi so that the aerodynamic reaction on thisaerofoil section is R1, which can bedecomposed into a lift Si and apropulsive force Ti.

Fig. 2 is a similar diagramfor the aerofoil section $2 of the otherblade 2 which is in a plane symmetrical of that of the plane of si withrespect .toa plane passing through YY and perpendicular to stem l.- Asabove explained, the tan- 3 gential velocity 02 of this section s2 is ofa direction opposed toithat of D1 but smaller in magnitude. Whencomposed with the aircraft velocity,

the resultant velocity is P2. Now P2 is so disposed with respect to thechord of section s2 that the aerodynamic reaction is R2 which decomposesinto a lift S2 and a horizontal force T2 of a direction, opposed to thatof propulsive force T but smaller than it.

element la'2a--l2a similar to the first 'one l2-l2 and at right anglesthereto. Annular part 12a is freely rotatable on a disc l3aeccentric-ally 'pivoted on axle l4. As the operation ,of unit l'a-2al2a--l3a is the same as that of' unit l'2-"l 2-4 3 only the latter willbe referred I to hereinafter. H

,1iftS1-l-s2 and a propulsive effort Ti-Tz.

Therefore these two sections have aerodynamic reactions which, whencomposed together, give a the'same is obviously true for all pairs ofcorresponding aerofoil cross sections, the aerodynamic unit l2. suppliesboth lift and horizontal p pulsion The same applies to unit Ill-2a.

What I claim is:

1. In combination with an aircraft, a frame carried by said aircraft, adriving rotary casing rotatable on said frame about a horizontal axis ofrotation fixed with respect to said frame, a rotor of the airscrew'typeincluding a stem extending at right angles to said horizontal axis andtwo blades carried by the opposed ends of said stem, means carried bysaid casing for slidably guiding said stem so that the stem axisconstantly intersects said horizontal axis of rotation of said casing,and a part piv'otally connected to said frame about a horizontal axisfixed with respect to said frame and located in the same horizontalplane as the first mentioned horizontal axis of rotation, to which it isparallel, this part being also pivotally connected to said stem about ahorizontal axis parallel to the two above mentioned axes of rotation.

2. In combination with an aircraft, a frame I carriedby said aircraft, adriving rotary casing rotatable on said frame about a horizontal axis ofrotation fixed with respect to said frame, a rotor of the airscrew typeincluding a stem ex tending at right angles to said horizontalaxis andtwo blades carried by the opposed ends of said stem, means carried bysaid casing'forslidably guiding said stem so that the'stem axisconstantly intersects said horizontal axis of rotation of said casing,and a part-pivotally connected to said frame about a horizontal axisfixed with respect to said frame and located in the same horizontalplane as the first mentioned horizontal axis of rotation, to which itisf'parallel, this part being also pivotally connected to said stemabout a horizontal axis parallel to the two above mentioned axes ofrotation, the distance between the first and second mentioned axes beingequal to that between the second and third mentioned axes. V

' GILBERT RICHARD.

REFERENCES CITED' The following references are of record in the file ofthis patent:

UNITED STATES PATENTS

